Design of integrated guidance-control (IGC) system for beam-riding guided missile

IGC system has drawn more and more attention, but most available research results are, in our opinion, not applicable to designing beam-riding guided missile. In our previous paper^[12], we use the IGC to design such a missile. Section 1 of the full paper summarizes the relevant results of Ref. 12. The core contents of section 2 include the following two points; (1)based on the transition matrix of the fourth-order state equations for IGC loop, we redefine the zero-effort miss(ZEM) of the guided missile without the need to calculate its time-to-go; (2)by choosing the ZEM as a single sliding mode surface, we design the integrated super-twisting second-order sliding mode guidance-control system. Section 3 simulates a certain missile. The simulation results, given in Figs. 1 through 6, show preliminarily that both the ZEM and the guidance range errors converge to zero in a finite time, indicating that our IGC design is effective. The discussion of simulation results, given in Figs. 7 through 9, verifies the advantages of our IGC design by comparing its results with those of the conventional method that designs guidance law and control system separately.